# Aircraft Builders Assoc DC10

- Type: Aircraft model (FAA registry)
- Registry code: 056259R
- Manufacturer (registry): AIRCRAFT BUILDERS ASSOC LLC
- Model: DC10
- Aircraft type: Fixed wing single engine
- Category: Airplane
- Engines: 1 · Reciprocating
- Seats: 4
- Weight class: Up to 12,499 lb
- Certification: Not type certificated
- Registered aircraft: 1
- Page: https://openairdocs.org/model/aircraft-builders-assoc-dc10

Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker.

## ADs that may apply (OpenAirDocs)

Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment.

None matched.

## Registered aircraft (1)

- [N46007](https://openairdocs.org/aircraft/N46007): [Aircraft Builders Associates LLC](https://openairdocs.org/faa-owner/AIRCRAFT%20BUILDERS%20ASSOCIATES%20LLC), [Tempe, AZ](https://openairdocs.org/faa-place/AZ/Tempe), built 2008, S/N 549702

## NTSB investigations

None matched to aircraft with this model.

## FAA accident and incident reports

None matched to aircraft with this model.

## Service difficulty reports (50)

As reported by operators and repair stations, by the model named in the report.

- [SDR WRLA2008072](https://openairdocs.org/sdr/WRLA2008072), Aug 26, 2008: BOLT. SHEARED. DURING C-CHECK INSPECTION FOUND 1 BOLT SHEARED AND RUSTED, AND 1 BOLT RUSTED AT RT WING ROOT FUSELAGE ANGLE. FUSELAGE STA 1371. REAMED HOLES, EDDY CURRENT INSPE
- [SDR 232587](https://openairdocs.org/sdr/232587), Mar 20, 2008: HOUSING. CRACKED. HOUSING IS CRACKED NEAR PRESSURE PORTS.
- [SDR CNMA20070006](https://openairdocs.org/sdr/CNMA20070006), Mar 18, 2007: CHANNEL. CORRODED. BS 2007, RBL 20-23, CORROSION ON CHANNEL SUPPORT UNDERNEATH GALLEY. CORRODED PORTION REMOVED NEW FABRICATED M/F S2920883-12000 AND INSTALLED WITH EXISTING FASTN
- [SDR 05FDEA02632](https://openairdocs.org/sdr/05FDEA02632), Aug 24, 2005: SKIN. CORRODED. BARE METAL AT CIRCUMFERENTIAL STRAP BETW. L40L & L41L FS 1871. REMOVED CORROSION,FABRICATED AND INSTALLED SHIM,DOUBLER,TRIPLER AND FINGER DOUBLERS IAW DC10-10/M
- [SDR 05FDEA01868](https://openairdocs.org/sdr/05FDEA01868), Jul 9, 2005: BRACKET. CRACKED. CTR WING LOWER STRUCTURE; RT BARREL STA 1277 INTERCOSTAL PRIMARY ATTACH BRACKET CRACKED. AS MARKED. ACCESS THRU CLG OR CAC. REMOVED AND REPLACED CRACKED BRACKET
- [SDR 05FDEA01867](https://openairdocs.org/sdr/05FDEA01867), Jul 9, 2005: BRACKET. CRACKED. CTR WING LOWER STRUCTURE; RT BARREL STRUCTURE STA 1237 INTERCOSTAL PRIMARY ATTACH BRACKET CRACKED THRU AS MARKED IN RED. ACCESS THRU CLG WHEEL WELL OR CAC0. REM
- [SDR 05FDEA00708](https://openairdocs.org/sdr/05FDEA00708), Mar 30, 2005: HINGE. CORRODED. LEFT WING INBOARD FLAP, OUTBOARD SUPPORT, PIVOT ATTACH POINT OUTBOARD BORE CORRODED. REMOVED CORROSION FROM BORE IAW DAC CMM 57-52-01. ALODINED AND PRIMED BORE 
- [SDR 05FDEA00706](https://openairdocs.org/sdr/05FDEA00706), Mar 30, 2005: SKIN. DAMAGED. RIGHT WING INBOARD FLAP, INCORRECT REPAIR ON UPPER SKIN, INBOARD WEDGE. REMOVED DOUBLER, FABRICATED NEW SKIN, FINGER DOUBLERS AND DOUBLER AND BONDED IAW FEDEX E
- [SDR 2005FA0000383](https://openairdocs.org/sdr/2005FA0000383), Mar 22, 2005: NOSE COWL. CORRODED. NOSE COWL SENT TO US FOR REPAIR. DURING EVALUATION SEVERE INTERGRANULAR CORROSION WAS DISCOVERED ON THE OUTER SKIN OF THE ACOUSTIC BARREL. SUSPECT IMPROPER HEAT
- [SDR 05FDEA00140](https://openairdocs.org/sdr/05FDEA00140), Jan 21, 2005: FRAME. DENTED. STATION 322 ON LEFT SIDE OF NOSE FUSELAGE JUST BELOW COCKPIT FLOOR FRAME IS DENTED. REFERENCE NON-ROUTINE N01203. COMPLIED WITH FEDEX EA 8-5310-83962,
- [SDR 05FDEA00141](https://openairdocs.org/sdr/05FDEA00141), Jan 21, 2005: SKIN. DENTED. FIRST OFFICERS PRIMARY STATIC PORT HAS EXTERNAL DOUBLER REPAIR WITHIN REDUCED VERTICAL SEPARATIONS. MINIMUN CONTROLLED AREA AT THE 9 TO 10 O'CLOCK POSITION PREV
- [SDR 05FDEA00139](https://openairdocs.org/sdr/05FDEA00139), Jan 21, 2005: HINGE. CORRODED. RIGHT WING INBOARD FLAP HINGE INBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMATER, FOUND TO BE OUT OF LIMITS IAW DAC CMM 57-52-01. ALODINE AND PRIME
- [SDR 05FDEA00138](https://openairdocs.org/sdr/05FDEA00138), Jan 21, 2005: HINGE. CORRODED. LEFT WING INBOARD FLAP HINGE INBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMETER, FOUND TO BE OUT OF LIMITS IAW DAC CMM 57-52-01, ALODINE AND PRIMED
- [SDR 05FDEA00137](https://openairdocs.org/sdr/05FDEA00137), Jan 21, 2005: BALANCE WEIGHT. CORRODED. RIGHT WING OUTBOARD AILERON 1 EACH BALANCE WEIGHT HAS CORROSION OUTBOARD SIDE OF ACTUATOR. REMOVED AND REPLACED RIGHT WING OUTBOARD AILERON BALANCE WEIGHT, BALA
- [SDR 05FDEA00136](https://openairdocs.org/sdr/05FDEA00136), Jan 21, 2005: HINGE. CORRODED. RIGHT WING INBOARD FLAP HINGE OUTBOARD PIVOT BUSHING GALLED AND PITTED. MEASURED BORE DIAMETER, FOUND TO BE OUT OF LIMITS IAW CMM 57-52-01, ALODINE AND PRIMED B
- [SDR 04FDEA03413](https://openairdocs.org/sdr/04FDEA03413), Dec 14, 2004: FITTING. CRACKED. CENTER ACCESSORY COMPARTMENT AT FUSELAGE STATION 1156 LT WING BOX FITTING IS CRACKED. REMOVED INNER ATTACHED ANGLE IAW DC10 SRM 51-33-01 VIL 2, FABRICATED REPAI
- [SDR 04FDEA02879](https://openairdocs.org/sdr/04FDEA02879), Oct 5, 2004: HINGE. CORRODED. LT WING OB FLAP IB HINGE, LOCATION NR 6, OB BORE IS CORRODED. REMOVED CORROSION, BEGINNING BORE DIAMETER 1.240, FINAL 1.266, MATERIAL LOSS 0.026 IAW DAC CMM 57-
- [SDR 04FDEA02802](https://openairdocs.org/sdr/04FDEA02802), Sep 22, 2004: SKIN. DAMAGED. NR 1 ENGINE IB COE COWL IS DAMAGED AT LEADING EDGE. REMOVED CORE COWL, CUT OUT DAMAGE, REMOVED FRAME AND RUBSTRIP, FABRICATED DOUBLER AND FILLER, DRILLED AND FI
- [SDR 04FDEA02647](https://openairdocs.org/sdr/04FDEA02647), Sep 4, 2004: PANEL. DEBONDED. FINGER DOUBLERS DISBONDED INSIDE LEFT WING TRAILING EDGE FAIRING BETWEEN XW 373 AND XORS 486, ACCESS THROUGH 641 MB. REMOVED ARC0584-1 SKIN FOR REPLACEMENT IAW 
- [SDR 04FDEA02644](https://openairdocs.org/sdr/04FDEA02644), Sep 4, 2004: PAN. GOUGED. NR 2 ENGINE RT FAN COWL INTERIOR HAS RUBBING APPROXIMATELY 8 INCHES ABOVE CENTER U-BOLT. REMOVED CENTER U-BOLT FITTING TO FOM. REMOVED DAMAGED SECTION OF PAN IA
- [SDR 04FDEA02348](https://openairdocs.org/sdr/04FDEA02348), Aug 2, 2004: FITTING. CORRODED. LOWER SFT WING TO CENTER BOX ATTACH SKI FITTING IS EXFOILATED. RIGHT WHEEL WELL STATION 1341 TO 1360 AT XCW 118. REMOVED ATTACHED STRUCTURE IAW DC10 SRM 51-33-0
- [SDR 04FDEA02345](https://openairdocs.org/sdr/04FDEA02345), Aug 2, 2004: SKIN. CORRODED. LOWER FUSELAGE UNDER WING BARREL SKIN IS CORRODED FROM STATION 1368 TO 1288 FROM LONGERON 47R TO 52R. REMOVED CORROSION IAW DC10 SRM 51-21-01 VOL II. ORIGINAL T
- [SDR 04FDEA001102](https://openairdocs.org/sdr/04FDEA001102), Apr 24, 2004: CONTROL UNIT. FAILED. ANTISKID FAILS (MULTIPLE REPEATS) REMOVED HUBCAPS, PERFORMED RINGOUT OF ALL WHEEL SPEED TRANSDUCERS, VALVES AND CONTROL WIRING, FOUND SHORT AT RECEPTACLE R5-264
- [SDR 04FDEA001101](https://openairdocs.org/sdr/04FDEA001101), Apr 24, 2004: SKIN. ERODED. RT OUTBOARD AILERON TRAILING EDGE, INBOARD END IS ERRODED. CUTOUT AND REPLACED DAMAGED SECTION, FABRICATED ZEE FOR REPAIR IAW DC-10 SRM 57-20-00 FIGURE 10 VOLUM
- [SDR 04FDEA001100](https://openairdocs.org/sdr/04FDEA001100), Apr 24, 2004: ALTIMETER. MALFUNCTIONED. FIRST OFFICERS RADIO ALTIMETER FLAG IN VIEW. AIRCRAFT CONTINUES TO DEVELOPE HISTORY OF RADIO ALTIMETER FAULTS. CLEANED RADIO ALTIMETER COOLING FANS AND R/T IAW 
- [SDR 04FDEA001099](https://openairdocs.org/sdr/04FDEA001099), Apr 24, 2004: SKIN. CRACKED. RT OUTBOARD AILERON INBOARD SUDE HAS SKIN SEPERATING AND CRACKED. FABRICATED NEW SKIN SECTION AND REPAIR DOUBLERS IAW DC-10 SRM 57-10-00 FIGURE 6 VOLUME 1. INST
- [SDR 04FDEA001098](https://openairdocs.org/sdr/04FDEA001098), Apr 24, 2004: DRUM. WRONG PART. LT SLAT DRIVE MECHANISM FOLLOWUP CABLW DRUM IS THE WRONG PART NUMBER. REMOVED AND REPLACE DRUM FOR LEFT HAND SLAT DRIVE MECHANISM IAW DAC CMM 27-83-11 PAGE 505 
- [SDR WRLA200401](https://openairdocs.org/sdr/WRLA200401), Jan 3, 2004: ASPIRATOR. SEPARATED. DURING MAINTENANCE CHECK, AT GSO, THE REQUIRED TEST DEPLOYMENT OF THE R1 DOOR EVACUATION SLIDE WAS ACCOMPLISHED. DURING TEST THE AFT ASPIRATOR OF THE SLIDE CAME
- [SDR WRLA200315](https://openairdocs.org/sdr/WRLA200315), Jun 16, 2003: SLIDE. MALFUNCTIONED. DURING A FUNCTIONAL CHECK OF RT FORWARD DOOR SLIDE ASSY (R1) DOOR FAILED TO OPEN TO ITS FULL TRAVEL. DOOR PNEUMATIC ACCUMULATOR BOTTLE NOTED TO HAVE BEEN AT LOW
- [SDR WRLA200312](https://openairdocs.org/sdr/WRLA200312), Jun 3, 2003: CONTROL PANEL. INOPERATIVE. AUTOPILOTS 1 AND 2 FAILED TO ENGATE RETURNED TO LAX, THE AIRCRAFT RETURNED TO THE DEPARTING STATION LAX FOR REPAIR. ALIGNED INU'S PRESSURIZED HYDRAULICS, YAW UP
- [SDR WRLA200302](https://openairdocs.org/sdr/WRLA200302), Feb 18, 2003: PRESSURE SWITCH. INOPERATIVE. NR 3 ENGINE OIL STRAINER CLOG CAME ON AFTER TAKEOFF LIGHT-SHUT DOWN ENGINE. IAW FLIGHT MANUAL PROCEDURES, RETURNED TO DEPARTURE STATION. REMOVED AND REPLACED NR
- [SDR F9B2002F00000](https://openairdocs.org/sdr/F9B2002F00000), Nov 20, 2002: DUCT. DAMAGED. INLET DUCT ASSEMBLY DAMAGED.
- [SDR 02FDEA00285](https://openairdocs.org/sdr/02FDEA00285), Apr 24, 2002: BOLT. CORRODED. RIGHT I/B FLAP O/B HINGE FWD BRACKET O/B H-11 BOLT CORRODED. R&R BOLTS PER EA 8-5750-60625.
- [SDR WRLA2002206](https://openairdocs.org/sdr/WRLA2002206), Mar 13, 2002: GCU. FAILED. DURING TAXI OUT, NR 3 GENERATOR OFF LIGHT ILLUMINATED NR 3 GENERATOR WAS RESET PER FCOM. DURING CLIMB APPROXIMATELY 15,000 FEET NR 3 GENERATOR VOLTS AND FREQUEN
- [SDR 20010129CW020](https://openairdocs.org/sdr/20010129CW020), Jan 2, 2001: SLIDE RAFT. MISINSTALLED. FOUND 8 FT LONG BY 2 INCHES WIDE, RED WEBBING STRAP TIED AROUND THE FOLDED INFLATABLE SLIDE/RAFT. IF THE UNIT WERE TO BE USED IN AN EMERGENCY, THE SLIDE WOULD N
- [SDR 00FDEA00885](https://openairdocs.org/sdr/00FDEA00885), Dec 16, 2000: TRANSMITTER. FAILED. 00-364 NR 3 ENGINE OIL TEMP GAGE MAXED OUT AT 200 DEG. SHUT DOWN NR 3 ENG IAW RED TAB PROC. RESECURED LOOSE CONNECTOR PLUG AND FAN COWLS.
- [SDR 20000712SH037](https://openairdocs.org/sdr/20000712SH037), Jul 12, 2000: SEAL. DAMAGED. ON TAKEOFF FROM ORD, ENGINE SUSTAINED SEVERE LPT DAMAGE RESULTING IN ATB. THE ENGINE HAD COMPLETED 833 HRS AND 341 CYCLES SINCE OVERHAUL. SUBSEQUENT STRIP INVES
- [SDR 00FDEA00418](https://openairdocs.org/sdr/00FDEA00418), Jul 1, 2000: SKIN. CORRODED. SKIN BULGING AROUND FASTENERS ON LWR SURFACE OF RT O/B AILERON. FOUND CORROSION BETWEEN SKIN AND FINGER DOUBLER. *S/D* REMOVED AND REPLACED LWR SURFACE SKIN OF 
- [SDR 20000426SH007](https://openairdocs.org/sdr/20000426SH007), Apr 3, 2000: RETAINER. DAMAGED. VISUAL INSPECTION SHOWED RING RETAINER AREA DAMAGED BEYOND LIMITS AND HEAVY CORROSION AT BOLT HOLE AREAS. (X)
- [SDR 99FDEA00312](https://openairdocs.org/sdr/99FDEA00312), Aug 4, 1999: SPAR. GOUGE. RIGHT WING AFT SPAR AFT TANG HAS A GOUGE ACROSS THE FLANGE AT XROS 414. COMPLIED WITH EA 8-5710-42395 RT REAR SPAR DEVIATION FROM EO 8-5710-7-30041.
- [SDR 98UAL900384](https://openairdocs.org/sdr/98UAL900384), Aug 5, 1998: TUBE. FAILED. SLIDE/RAFT HAD A SEAM FAILURE ON THE LOWER TUBE AFTER FLAT FIRE TEST DURING UNIT OVERHAUL. SCRAPPED UNIT.
- [SDR 98ZZZX844](https://openairdocs.org/sdr/98ZZZX844), Feb 11, 1998: VALVE BODY. CRACKED. HAD SEVERAL INSTANCES WHERE FLIGHT CONTROL VALVE BODY WAS CRACKED. CRACK IS LOCATED IN THREAD RELIEF AREA.
- [SDR 98ZZZX843](https://openairdocs.org/sdr/98ZZZX843), Feb 11, 1998: VALVE BODY. CRACKED. FLIGHT CONTROL BYPASS VALVE HAS HAD SEVERAL INSTANCES WHERE THE VALVE BODY HAS BEEN CRACKED. VALVE CRACKED IN RADIUS BETWEEN INSIDE DIAMETER AND BOTTOM OF BODY.
- [SDR 97ZZZX4715](https://openairdocs.org/sdr/97ZZZX4715), Oct 27, 1997: PUMP. DAMAGED. PUMP RETURNED FOR OVERHAUL AND SB COMPLIANCE. FOUND BEYOND REPAIR AND FOD BOLT WAS WEDGED BETWEEN VANES OF IMPELLER SECTION ALONG WITH WASHER FRAGMENTS. INTERNA
- [SDR 97ZZZX3907](https://openairdocs.org/sdr/97ZZZX3907), Aug 27, 1997: RESISTOR. FAILED. RESISTORS FAILED CAUSING CSD LOAD CONTROLLER TO FAIL AND MAINTAIN PROPER CYCLES. THIS IS THE SECOND TYPE OF THIS FAILURE. ORIGINAL PARTS CAME FROM MANUFACTURER.
- [SDR 97ZZZX3906](https://openairdocs.org/sdr/97ZZZX3906), Aug 27, 1997: RESISTOR. FAILED. RESISTORS FAILED CAUSING CSD LOAD CONTROLLER TO FAIL AND MAINTAIN PROPER CYCLES. THIS IS THE SECOND TYPE OF THIS FAILURE. ORIGINAL PARTS CAME FROM MANUFACTURER.
- [SDR 97ZZZX3757](https://openairdocs.org/sdr/97ZZZX3757), Aug 13, 1997: STATOR HOUSING. OVERSIZED. DURING DISASSEMBLY OF BEARING LINER FROM THE HOUSING, A SHIM WAS FOUND AROUND THE HOUSING INSIDE DIAMETER WHERE THE BEARING LINER SITS. THE HOUSING I.D. WHERE B
- [SDR 96ZZZX4137](https://openairdocs.org/sdr/96ZZZX4137), Jul 16, 1996: DUCT. FLANGE BROKEN. THE DUCT WAS RECEIVED WITH ONE FLANGE RUPTURED AT A PREVIOUS WELD REPAIR LOCATION. ALL OTHER HIDDEN DAMAGE INSPECTION TO THE DUCT ASSEMBLY DID NOT REVEAL ANY SU
- [SDR 96ZZZX2370](https://openairdocs.org/sdr/96ZZZX2370), Apr 11, 1996: FITTING. CORRODED. HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. THIS IS WHAT ATTACHES THE VANE TO THE FLA
- [SDR 96ZZZX2369](https://openairdocs.org/sdr/96ZZZX2369), Apr 11, 1996: FITTING. CORRODED. HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. THIS IS WHAT ATTACHES THE VANE TO THE FLA

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